CN106253161A - A kind of composite material cable cover - Google Patents
A kind of composite material cable cover Download PDFInfo
- Publication number
- CN106253161A CN106253161A CN201610871712.XA CN201610871712A CN106253161A CN 106253161 A CN106253161 A CN 106253161A CN 201610871712 A CN201610871712 A CN 201610871712A CN 106253161 A CN106253161 A CN 106253161A
- Authority
- CN
- China
- Prior art keywords
- cover body
- rubber blanket
- cover
- aircraft
- composite material
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02G—INSTALLATION OF ELECTRIC CABLES OR LINES, OR OF COMBINED OPTICAL AND ELECTRIC CABLES OR LINES
- H02G3/00—Installations of electric cables or lines or protective tubing therefor in or on buildings, equivalent structures or vehicles
- H02G3/02—Details
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02G—INSTALLATION OF ELECTRIC CABLES OR LINES, OR OF COMBINED OPTICAL AND ELECTRIC CABLES OR LINES
- H02G3/00—Installations of electric cables or lines or protective tubing therefor in or on buildings, equivalent structures or vehicles
- H02G3/02—Details
- H02G3/03—Cooling
Landscapes
- Engineering & Computer Science (AREA)
- Architecture (AREA)
- Civil Engineering (AREA)
- Structural Engineering (AREA)
- Insulating Bodies (AREA)
Abstract
The invention provides a kind of composite material cable cover, including front cover body, front rubber blanket, middle cover, rear cover body and rear rubber blanket, before and after thin shell type, cover body two ends of repelling each other are streamlined curved surface, and opposite end is by middle cover connection, side is installed surface protruding laterally, is used for connecting aircraft；Front and back rubber blanket is arranged between before and after's cover body and aircraft, and the rear end of rear rubber blanket has gap, for keeping the air pressure balance inside and outside whole cable hood.Present configuration is simple, uses mould molding accurate；Easy to install, reliability is high；Required precision to part key dimension is the highest, can meet requirement, reduce production cost, improve production efficiency under the conditions of common production.
Description
Technical field
The present invention relates to materialogy and mechanics field, especially a kind of composite material cable cover.
Background technology
During spacecraft high-speed flight in an atmosphere, windstream and aircraft can produce friction so that nacelle surface
Temperature raises, and causes Aerodynamic Heating.In order to protect outer surface to protect across the cable of cabin section, the forms using cable hood more.
Cable hood is in nacelle outer surface protruding parts, and Aerodynamic Heating is more serious than other sections, simultaneously cable hood internally installed have multiple
Remote-measuring equipment and control cable, when nacelle is by Aerodynamic Heating, cable hood should have good pneumatic thermal protective performance, to ensure to set
Getting everything ready good working environment, do not lost efficacy because of high temperature failure, therefore first the design principle of cable hood is intended to carry out
The design of heat insulation material and type selecting, it is secondary has rational aerodynamic configuration.
As a kind of product with complex profile, how to guarantee to meet the use requirement of cable hood, will not lose because of material
Effect or stress excessive generation crack, profile junction, even affect the service behaviour of internal unit cable, be that spacecraft grinds
Major issue to be considered during system.Generally material many selections metal material of cable hood, outer surface spraying solar heat protection
Coating.If this type of cable hood is designed to when obtaining certain anti-thermal effect, but structure is complicated, processing difficulties, and cost is high,
The concordance of product is difficult to ensure that.Some employing steel plate reinforcement formula structures, heavier mass, machining is complicated, and versatility is bad.
Summary of the invention
In order to overcome the deficiencies in the prior art, the present invention provides a kind of composite material cable cover, with low cost, processing technique
Property is good, and lighter weight, homogeneity of product is easily guaranteed that, and goes for the aircraft of different structure form.
The technical solution adopted for the present invention to solve the technical problems is: a kind of composite material cable cover, including front cover body,
Front rubber blanket, middle cover, rear cover body and rear rubber blanket.
With aircraft direction of advance as front end, described front cover body is shell construction, and thickness is 4～6mm, and front end is stream
Line style curved surface, side is installed surface protruding laterally, is used for connecting aircraft；Described rear cover body is shell construction, thick
Degree is 4～6mm, and rear end is streamlined curved surface, and side is installed surface protruding laterally, is used for connecting aircraft；In described
The channel that cover is thick 4～6mm, two ends are respectively communicated with the rear end of front cover body and the front end of rear cover body；Described front rubber blanket
Being arranged between front cover body and aircraft, seal front end and the both sides of front cover body, thickness is 2～5mm；Described rear rubber blanket peace
Being contained between front cover body and aircraft, thickness is 2～5mm, and the rear end of rear rubber blanket has gap, is used for keeping whole cable hood
Inside and outside air pressure balance.
The material of described front cover body, middle cover and rear cover body is high silicone/phenolic resin glass cloth or carbon/phenolic aldehyde cloth；Described
The material of front rubber blanket and rear rubber blanket is Silicone Rubber Coated fabric or silicone rubber glass cloth.
Described front cover body is through prepreg then laying die forming, or uses braiding to shape and resin transfer moulding
Method shapes；Described middle cover uses laying cure under pressure to shape.
Between described front cover body and front rubber blanket, rear cover body and rear rubber blanket use room temperature vulcanized silicone rubber GD414 or
Silicone rubber 703 is bonding.
Described front cover body, the abutment joint between middle cover and rear cover body use room temperature vulcanized silicone rubber GD414 to seal
Process.
The invention has the beneficial effects as follows:
(1) simple in construction, uses mould molding accurate；
(2) easy to install, reliability is high；
(3) required precision to part key dimension is the highest, can meet requirement, reduce production under the conditions of common production
Cost, improves production efficiency.
Accompanying drawing explanation
Fig. 1 is the structural representation of the present invention；
Fig. 2 is the structural representation of front cover body；
Fig. 3 is the structural representation of front rubber blanket；
Fig. 4 is the structural representation of middle cover；
Fig. 5 is the structural representation of rear cover body；
Fig. 6 is the structural representation of rear rubber blanket；
In figure, cover body before 1-, rubber blanket before 2-, covers in 3-, 4-rear cover body, rubber blanket after 5-.
Detailed description of the invention
The present invention is further described with embodiment below in conjunction with the accompanying drawings, and the present invention includes but are not limited to following enforcement
Example.
The composite material cable cover that the present invention provides is a kind of structural member with complicated streamline curved surface, is arranged on space and flies
Row device outer surface, is used for protecting the cable by spacecraft outer surface, makes cable not affected by aerodynamic force and Aerodynamic Heating.
This composite material cable cover can greatly reduce processing link, removes spraying heat-resistant paint link, raises labour productivity, alleviate
Construction weight, possesses again the characteristic at high temperature worked long hours, and can meet structural strength and thermal environment requirement simultaneously.
In order to install composite material cable cover easily at aircraft outer surface, also meet the machinability of technique simultaneously,
The stagewise composite material cable cover that the present invention provides is as it is shown in figure 1, by front cover body 1, front rubber blanket 2, middle cover 3, rear cover body 4 and
Rear rubber blanket 5 forms.Front cover body 1 is shell construction, and front end is streamlined curved surface, and side is installed surface, and its structure is shown in Fig. 2.
The thickness of front cover body 1 is 4～6mm, and installed surface can be processed 8～10 counter sinks, with the screw that specification is M5, M6 or M8 with fly
Row device connects.Front cover body 1 can use high silicone/phenolic resin glass cloth or carbon/phenolic aldehyde cloth, is molded into through prepreg then laying
Shape, it would however also be possible to employ knitting forming shapes with resin transfer molding practice.Front rubber blanket 2 thickness is 2～5mm, and its structure is shown in Fig. 3.
Material can use Silicone Rubber Coated fabric or silicone rubber glass cloth, has the most flexible and ablation resistance, with here playing
Sealing function, the cable in protection cable hood.Front cover body 1 can use room temperature vulcanized silicone rubber GD414 or silicon rubber with front rubber blanket 2
Glue 703 is bonding.Middle cover 3 is 4～6mm thick channels, sees Fig. 4.High silicone/phenolic resin glass cloth or carbon/phenolic aldehyde cloth, warp can be used
Cross manual laying cure under pressure to shape.16～20 through holes can be processed on the installed surface of middle cover 3, be M5, M6 or M8 by specification
Screw is connected with aircraft.Rear cover body 4 uses and the front identical version of cover body 1, and its structure is shown in Fig. 5.Rear rubber blanket 5
Thickness is 2～5mm, and its structure is shown in Fig. 6.Material can use Silicone Rubber Coated fabric or silicone rubber glass cloth, and rear rubber blanket 5 is with front
The difference of rubber blanket 1 is that rear portion has the gap of a 20mm, for keeping the air pressure balance inside and outside whole cable hood.
The cable hood assembly method of the present invention is: front cover body 1 and bonding front rubber blanket 2 are fixed on 8 screws and fly
In row device nacelle, middle cover 3 is fixed on 9 centering cover hold-down supports of aircraft nacelle outer surface with 18 screws, rear cover body 4 He
Bonding rear rubber blanket 5 is fixed in aircraft nacelle with 8 screws, afterwards with room temperature vulcanized silicone rubber GD414 to cover body
Between abutment joint carry out encapsulation process.
In the development process of certain spacecraft cable hood, totally the requirement to cable hood Aerodynamic Heating is the harshest,
Requirement cable hood can bear Aerodynamic Heating during boosting flight, and its thermal protection struc ture should have good heat stability, Qi Zhong electricity
Cable cover leading head momentary surroundings temperature is the highest 1160 DEG C, and main environment temperature is 600 DEG C.By composite and curved surface are tied
The analytical calculation of configuration formula, is designed to version as shown in Figure 1 by cable hood.Cable hood is stagewise combining form, by
Front cover body 1, front rubber blanket 2, middle cover 3, rear cover body 4 and rear rubber blanket 5 form.Front cover body 1 is shell construction, and front end is streamline
Type curved surface, side is installed surface, and its structure is shown in Fig. 2.The thickness of front cover body 1 is 4, a length of 300mm, and width is 90mm, high
Degree is 25mm, installed surface machined the counter sink of 8 Φ 5.5mm, be fixed on aircraft cabin with the screw (standard component) of 8 M5
On body.Front cover body 1 uses high silicone/phenolic resin glass cloth through prepreg overlay die forming.Front rubber blanket 2 thickness is 2mm, its
Structure is shown in Fig. 3.Material uses silicone rubber glass cloth, with here playing sealing function.Front cover body 1 uses room temperature with front rubber blanket 2
Sulphurated siliastic GD414 is bonding.Middle cover 3 is the channel that 4mm is thick, a length of 2700mm, and width is 90mm, and height is 26mm,
Structure is shown in Fig. 4.High silicone/phenolic resin glass cloth is used to shape through manual laying cure under pressure.Machined on the installed surface of middle cover 3
The through hole of 16 Φ 5.5mm, is that M5 screw (standard component) is fixed on aircraft nacelle bearing by specification.Rear cover body 4 use with
The front identical material of cover body 1 and version, a length of 270mm, width is 90mm, and height is 25mm, and its structure is shown in figure
5.Rear rubber blanket 5 thickness is 2mm, and its structure is shown in Fig. 6.Material uses silicone rubber glass cloth, has slitting of a 20mm at rear portion
Mouthful, for keeping the air pressure balance inside and outside whole cable hood.Whole cable hood is pacified by the screw (standard component) of 32 M5 × 20
It is contained in aircraft outer surface.
After the real flight test of aircraft, the temperature recording cable hood front end cambered surface inner surface is 225 DEG C, meets
The cable operating temperature of general requirement have to be lower than the requirement of 300 DEG C.From the successful result of flight test it can be seen that conduct
One load/thermal protection struc ture part, composite material cable cover on non-recurring structure unstability in whole flight course, rupture, destruction etc.
Situation, has withstood the true Airflow Environment of flight test and the examination of thermal environment completely, has fully demonstrated this composite material cable
The technical feasibility of cover and reliability.
Claims (5)
1. a composite material cable cover, including front cover body, front rubber blanket, middle cover, rear cover body and rear rubber blanket, its feature exists
In: with aircraft direction of advance as front end, described front cover body is shell construction, and thickness is 4～6mm, and front end is streamlined
Curved surface, side is installed surface protruding laterally, is used for connecting aircraft；Described rear cover body is shell construction, and thickness is 4
～6mm, rear end is streamlined curved surface, and side is installed surface protruding laterally, is used for connecting aircraft；Described middle cover is thick
The channel of 4～6mm, two ends are respectively communicated with the rear end of front cover body and the front end of rear cover body；Described front rubber blanket is arranged on
Between front cover body and aircraft, sealing front end and the both sides of front cover body, thickness is 2～5mm；Before described rear rubber blanket is arranged on
Between cover body and aircraft, thickness is 2～5mm, and the rear end of rear rubber blanket has gap, for keeping inside and outside whole cable hood
Air pressure balance.
Composite material cable cover the most according to claim 1, it is characterised in that: described front cover body, middle cover and rear cover body
Material be high silicone/phenolic resin glass cloth or carbon/phenolic aldehyde cloth；Described front rubber blanket and the material of rear rubber blanket are that silicone rubber is coated with
Cover fabric or silicone rubber glass cloth.
Composite material cable cover the most according to claim 1, it is characterised in that: described front cover body is through prepreg then
Laying die forming, or use braiding to shape and resin transfer molding practice shaping；Described middle cover uses laying cure under pressure
Shape.
Composite material cable cover the most according to claim 1, it is characterised in that: described front cover body and front rubber blanket it
Between, rear cover body and rear rubber blanket use room temperature vulcanized silicone rubber GD414 or silicone rubber 703 bonding.
Composite material cable cover the most according to claim 1, it is characterised in that: described front cover body, middle cover and rear cover body
Between abutment joint use room temperature vulcanized silicone rubber GD414 carry out encapsulation process.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610871712.XA CN106253161A (en) | 2016-09-30 | 2016-09-30 | A kind of composite material cable cover |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610871712.XA CN106253161A (en) | 2016-09-30 | 2016-09-30 | A kind of composite material cable cover |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106253161A true CN106253161A (en) | 2016-12-21 |
Family
ID=57611301
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610871712.XA Pending CN106253161A (en) | 2016-09-30 | 2016-09-30 | A kind of composite material cable cover |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106253161A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107959266A (en) * | 2018-01-05 | 2018-04-24 | 北京航空航天大学 | Embedded sectional type cable cover |
| CN110466737A (en) * | 2019-08-19 | 2019-11-19 | 西安长峰机电研究所 | A kind of composite material nose fairing |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201122815Y (en) * | 2007-11-20 | 2008-09-24 | 谢步明 | Protecting equipment used for experiment station temporary cable |
| CN202333648U (en) * | 2010-12-31 | 2012-07-11 | 青岛造船厂有限公司 | Cable protecting cover for boat |
| EP2574542A2 (en) * | 2011-09-27 | 2013-04-03 | Airbus Operations GmbH | Fuselage cell for an aircraft, particularly an airplane |
| CN204223186U (en) * | 2014-10-23 | 2015-03-25 | 北京宇航系统工程研究所 | A kind of light thin-wall composite structure fairing |
| CN204517315U (en) * | 2015-05-04 | 2015-07-29 | 中冶建工集团有限公司 | Temporary electricity usage in construction sites cable protective sleeve |
| CN205393331U (en) * | 2016-03-15 | 2016-07-27 | 中国航天科工集团第六研究院二一○所 | Aircraft radome fairing forming device |
-
2016
- 2016-09-30 CN CN201610871712.XA patent/CN106253161A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201122815Y (en) * | 2007-11-20 | 2008-09-24 | 谢步明 | Protecting equipment used for experiment station temporary cable |
| CN202333648U (en) * | 2010-12-31 | 2012-07-11 | 青岛造船厂有限公司 | Cable protecting cover for boat |
| EP2574542A2 (en) * | 2011-09-27 | 2013-04-03 | Airbus Operations GmbH | Fuselage cell for an aircraft, particularly an airplane |
| CN204223186U (en) * | 2014-10-23 | 2015-03-25 | 北京宇航系统工程研究所 | A kind of light thin-wall composite structure fairing |
| CN204517315U (en) * | 2015-05-04 | 2015-07-29 | 中冶建工集团有限公司 | Temporary electricity usage in construction sites cable protective sleeve |
| CN205393331U (en) * | 2016-03-15 | 2016-07-27 | 中国航天科工集团第六研究院二一○所 | Aircraft radome fairing forming device |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107959266A (en) * | 2018-01-05 | 2018-04-24 | 北京航空航天大学 | Embedded sectional type cable cover |
| CN107959266B (en) * | 2018-01-05 | 2020-06-19 | 北京航空航天大学 | Embedded sectional type cable cover |
| CN110466737A (en) * | 2019-08-19 | 2019-11-19 | 西安长峰机电研究所 | A kind of composite material nose fairing |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| KR102412502B1 (en) | Wing and method of manufacturing | |
| EP2354494B1 (en) | Turbomachine Nacelle And Anti-Icing System And Method Therefor | |
| EP2354469B1 (en) | Turbomachine Nacelle And Anti-Icing System And Method Therefor | |
| US9738375B2 (en) | One-piece composite bifurcated winglet | |
| US6478922B1 (en) | Method of manufacturing a composite structure using a conformable locating aperture system | |
| US9643733B2 (en) | Fire seal for an aircraft | |
| US20090064681A1 (en) | Scalloped Flexure Ring | |
| US9279531B2 (en) | Composite ducts and methods | |
| CN202329435U (en) | Multilayer-structured heat-insulating integrated cabin section | |
| US20190039746A1 (en) | Acoustic honeycomb panel with integrated electrical heater | |
| US20220411077A1 (en) | Electrothermal heater mat | |
| US10953624B2 (en) | Aircraft airfoil having a stitched trailing edge and manufacturing method thereof | |
| CN106253161A (en) | A kind of composite material cable cover | |
| CN110654526A (en) | Temperature equalizing method and structure for high-temperature and high-heat part | |
| CN204223186U (en) | A kind of light thin-wall composite structure fairing | |
| US10863586B2 (en) | Electrical conductive resin matrix for CNT heater | |
| CN210653691U (en) | Fairing and aerospace craft | |
| CN109606614A (en) | A kind of aircraft wing inspection socket regional structure design method | |
| CN110466737A (en) | A kind of composite material nose fairing | |
| CN110723275A (en) | High-temperature heat-proof opening cover structure | |
| CN212931909U (en) | Technological air inlet channel and aero-engine experimental platform | |
| CN103818053A (en) | In-mold metallization of composite structures | |
| EP3160705B1 (en) | A thermally expansive molding tool and a method of molding with such tool | |
| Gessenharter et al. | Optimization of Assembly Processes by Heated Air Technology | |
| Keck et al. | Design, analysis, and manufacturing of a carbon-fibre-reinforced polyetheretherketone slat |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20161221 |